Weather-resistant unmanned aerial vehicles, and associated systems and methods

Abstract

The present technology is directed to an unmanned aerial vehicle (UAV) a wing. The UAV can include first and second propellers extending from a front portion of the wing and positioned to provide thrust to the UAV. The UAV can include a first actuator carried by the wing, and a first leg operably coupled to the first actuator. The first leg can be configured to rotate in a first plane parallel to a plane bisecting the wing. In some embodiments, the UAV includes a second leg connected to a second actuator, the second leg configured to rotate in a plan parallel to the first plane.

1 . An unmanned aerial vehicle (UAV) comprising:
 a wing having—
 a front portion; 
 a rear portion opposite the front portion; 
 a first lateral portion extending from the front portion to the rear portion; 
 a second lateral portion opposite the first lateral portion and extending from the front portion to the rear portion; 
 an upper surface extending from the front portion to the rear portion and from the first lateral portion to the second lateral portion; and 
 a lower surface opposite the upper surface and extending from the front portion to the rear portion and from the first lateral portion to the second lateral portion; 
   a first propeller extending from the front portion away from the rear portion, the first propeller having a first axis of rotation and positioned to provide thrust to the UAV in a direction parallel to the first axis of rotation;   a second propeller extending from the front portion away from the rear portion and positioned between the first propeller and the second lateral portion of the wing, the second propeller having a second axis of rotation and positioned to provide thrust to the UAV in a direction parallel to the second axis of rotation;   a first actuator carried by the wing; and   a first leg operably coupled to the first actuator and configured to rotate in a first plane parallel to a plane bisecting the wing through the front portion and the upper surface.   
     
     
         2 . The UAV of  claim 1 , further comprising:
 a second actuator carried by the wing; and   a second leg operably coupled to the second actuator and configured to rotate in a second plane parallel to the first plane   
     
     
         3 . The UAV of  claim 1  wherein the first leg comprises a hook feature on an end of the first leg opposite the first actuator. 
     
     
         4 . The UAV of  claim 1  wherein the first actuator is configured to rotate the first leg between a retracted position and a deployed position, wherein the first leg is positioned entirely within the wing in the stowed position, and wherein the first leg extends from the wing in a direction opposite the rear portion and opposite the upper surface in the deployed position. 
     
     
         5 . The UAV of  claim 1  wherein the first actuator is positioned within the wing. 
     
     
         6 . The UAV of  claim 2  wherein:
 the first plane is coplanar with the second plane; 
 the first actuator is positioned between the second actuator and the front portion of the wing; 
 the second actuator is configured to rotate the second leg between a stowed position and a deployed position; 
 the second leg is positioned entirely within the wing in the stowed position; and 
 the second leg extends from the wing in a direction opposite the front portion and opposite the upper surface in the deployed position. 
 
     
     
         7 . The UAV of  claim 1 , further comprising:
 a first stabilizer connected to the first lateral portion of the wing, the first stabilizer extending above the upper surface and below the lower surface at the rear portion of the wing; and   a second stabilizer connected to the second lateral portion of the wing, the second stabilizer extending above the upper surface and below the lower surface at the rear portion of the wing.   
     
     
         8 . The UAV of  claim 7  wherein the first stabilizer extends from the front portion to the rear portion of the wing, and wherein the second stabilizer extends from the front portion to the rear portion of the wing. 
     
     
         9 . The UAV of  claim 7  wherein the first stabilizer has a shape that matches a profile of the wing from the front portion to a position 20% toward the rear portion when observed in a direction normal to a plane that bisects the wing between the first lateral portion and the second lateral portion. 
     
     
         10 . The UAV of  claim 2  wherein the first is configured to grasp the ground when the UAV is landed. 
     
     
         11 . The UAV of  claim 1 , further comprising one or more battery cells within the wing and one or more solar panels on the upper surface of the wing configured to charge the one or more battery cells. 
     
     
         12 . The UAV of  claim 11  wherein the one or more solar panels cover at least 75% of the upper surface of the wing. 
     
     
         13 . The UAV of  claim 11  wherein the one or more solar panels cover at least 90% of the upper surface of the wing. 
     
     
         14 . The UAV of  claim 11  wherein the first leg and/or the second leg are configured to tilt the wing to change an angle between the sun and the solar panels when the UAV is landed. 
     
     
         15 . The UAV of  claim 1  wherein the wing comprises a first elevon and a second elevon at the rear portion of the wing. 
     
     
         16 . The UAV of  claim 15  wherein the first and second elevons span the entire rear portion. 
     
     
         17 . The UAV of  claim 15  wherein the first elevon spans a first half of the rear portion and the second elevon spans a remaining half of the rear portion. 
     
     
         18 . The UAV of  claim 15 , further comprising a solar panel carried by the first elevon. 
     
     
         19 . The UAV of  claim 1  wherein the first leg and/or the second leg are telescoping. 
     
     
         20 .- 33 . (canceled) 
     
     
         34 . An unmanned aerial vehicle (UAV) comprising:
 a wing having—
 an upper surface; and 
 a lower surface opposite the upper surface; 
   a first propeller extending forward from a front portion of the wing and positioned to provide thrust to the UAV;   a second propeller extending forward from the front portion of the wing and positioned to provide thrust to the UAV;   a first actuator connected to the wing;   a first leg operably connected to the first actuator and configured to rotate in a first plane parallel to a plane bisecting the wing through the front portion and the upper surface; and   one or more solar panels carried by the wing and covering at least 75% the upper surface of the wing.   
     
     
         35 . The UAV of  claim 34  wherein the one or more solar panels cover at least 90% of the upper surface of the wing. 
     
     
         36 . The UAV of  claim 34 , further comprising:
 a first stabilizer positioned at a first side of the wing, the first stabilizer extending above the upper surface and below the lower surface at a rear portion of the wing; and   a second stabilizer positioned at a second side of the wing, the second stabilizer extending above the upper surface and below the lower surface at the rear portion of the wing.   
     
     
         37 . The UAV of  claim 36  wherein the first stabilizer comprises a first portion and a second portion connected to the first portion at a first hinge, and wherein the first portion is configured to articulate in a direction away from the lower surface of the wing before the UAV takes off from the ground. 
     
     
         38 . The UAV of  claim 37  wherein the second stabilizer comprises a first portion and a second portion connected to the first portion at a second hinge, and wherein the first portion is configured to articulate in a direction away from the lower surface of the wing before the UAV takes off from the ground. 
     
     
         39 . The UAV of  claim 38  wherein the wing comprises a first elevon and a second elevon at the rear portion of the wing. 
     
     
         40 . The UAV of  claim 39  wherein the first elevon is configured to articulate parallel to the first portion of the first stabilizer before the UAV takes off from the ground, and wherein the second elevon is configured to articulate parallel to the first portion of the second stabilizer before the UAV takes off from the ground. 
     
     
         41 . The UAV of  claim 34  wherein the first propeller is configured to tilt in a direction parallel to a plane that bisects the wing through the upper and lower surfaces. 
     
     
         42 . The UAV of claim  46  wherein the second propeller is configured to tilt in a direction parallel to the plane that bisects the wing through the upper and lower surfaces.